THERMAL DESIGN OF RETURNABLE SATELLITE

Abstract

Abstract: This paper presents the thermal control subsystem of chinese returnable satellite. According to the characteristics of the satellite, a method of thermal inertia used in thermal design is described.The temperatures obtained from orbit telemetry data are in agreement with that from ground testing.Thermal control subsystem operated well the temperatures of the structure and the equipments met the design requirement.

Key words: Recoverable satellite, Temperature control, Thermodynamic test, Thermal analysis, Design

Xu Jiwan (Beijing Institute of Spacecraft Systems Engineering). THERMAL DESIGN OF RETURNABLE SATELLITE[J]. Chinese Space Science and Technology.

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URL: https://journal26.magtechjournal.com/kjkxjs/EN/

https://journal26.magtechjournal.com/kjkxjs/EN/Y1990/V10/I06/49

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